Dynamic simulation of stick–slip motion of a flexible solar array

The scope of this paper is to present an analytical approach to the stick–slip of the tension control mechanism (TCM) by means of spacecraft attitude responses. The mathematical model utilized assumes that the spacecraft was composed of a main rigid body and flexible appendages, which consist of a number of rigid plates connected by torsional hinges. Key parameters of the hinges are determined by applying the equations of the vibration of a uniform cantilever beam with tangible physical parameters. This mathematical model was evaluated using the ADEOS and ADEOS-II flight data and ground-based test data. It is concluded that the technical approach and mathematical model utilized have correctly represented actual spacecraft motions.